Variable volume burning rate test device for propellant

Abstract

The invention discloses a propellant powder volume variation combustion speed testing device. The propellant powder volume variation combustion speed testing device comprises a body component, an ignition component, a first pressure sensor, a second pressure sensor, a data collecting and processing system and a high-speed camera component. The device can simulate the motion environment in a barrel weapon chamber, and can obtain the combustion speed data of propellant powder under conditions of high-speed motion and volume variation, thereby providing reliable input data for the development of propellant powder and weapon powder charging design; the technical problem that the pressure at the bottom of a bullet cannot be measured directly so far is solved, which is crucial to the analysis of an internal trajectory for charging powder and combustion in a chamber of propellant powder.

Description

technical field [0001] The invention belongs to the field of propellant performance testing, and mainly relates to a propellant combustion performance test device, in particular to a device capable of testing the variable volume burning rate of propellant propellant moving at high speed under airtight conditions. Background technique [0002] The propellant is the power source for the barrel weapon to complete the projectile launch. Its combustion performance directly determines the initial velocity of the projectile, the life of the weapon barrel and the stability of the barrel weapon launch. In the development process of gunpowder for body-tube weapons, the burning rate of propellant is generally tested by the closed detonator test method to evaluate the combustion performance of propellant. Since the airtight detonator used in the test is a constant volume test device, there are generally 100ml, 200ml, 500ml and 800ml models, these different types of airtight detonators c...

AI Technical Summary

Problems solved by technology

Therefore, there are the following problems in testing the burning speed of the propellant by the detonator test method: (1) When the propellant burns, it basically remains in a static state, which is inconsistent with the condition that the propellant burns at a certain speed in practical applications

From the technical information retrieved so far, there is no public report on the burning rate test of the propellant under the condition of airtight and high-speed motion of the propellant

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